Automatic mass center adjusting device of aero-engine bearing rotor system

Abstract

The invention belongs to the technical field of aero-engine rotor balance, and provides an aero-engine bearing rotor system mass center automatic adjusting device which comprises circular ring bases, shaft necks at the two ends of a bearing rotor are sleeved with the circular ring bases, a plurality of adjusting mechanisms are arranged on the circular ring bases in the circumferential direction, balance weight loading blocks are arranged on the adjusting mechanisms, and the balance weight loading blocks are arranged on the bearing rotor. When the aero-engine bearing rotor rotates, the distance between the balance weight loading block on each adjusting mechanism and the axis of the bearing rotor is adjusted in a self-adaptive mode, so that the axis and the mass center of the bearing rotor basically coincide. According to the device, dynamic self-balancing of the rotor is achieved through a pure mechanical coupling mechanism of centrifugal force-elastic deformation-lever displacement, centripetal force is applied to the balance weight loading block during passing, the distance between the balance weight loading block and the circular ring base is dynamically adjusted, the unbalance amount is effectively reduced, more accurate balance correction and self-adaptive balance weight adjustment of the rotor are achieved, and the dynamic self-balancing effect of the rotor is improved. The operation stability of the aero-engine rotor is improved, and the labor cost and the time cost are greatly reduced.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aero-engine rotor balancing, and relates to a center of mass automatic adjusting device of a bearing rotor system of an aero-engine. BACKGROUND

[0002] In the field of aviation, as the "heart" of an airplane, the performance and reliability of an aero-engine directly relate to flight safety and overall performance. As one of the core components of an aero-engine, a rotor inevitably produces uneven mass distribution, i.e., rotor imbalance, due to material unevenness, machining and assembly errors or wear and tear during high-speed operation. Such imbalance will cause severe vibration under high-speed rotation. It has been proved by practice that rotor imbalance is the main cause of vibration exceeding the limit during engine operation, which directly leads to increased engine noise, accelerated bearing wear and shortened service life of the engine.

[0003] At present, the method for solving rotor imbalance mainly relies on manual balancing correction. An operator needs to place the rotor on a professional balancing test device or through a simulation method to eliminate the imbalance by measuring and adjusting the position of the balancing block for multiple times. This process is tedious and time-consuming, requires experienced technicians to operate, has large correction errors, and the method is a passive correction method, which may still cause rotor imbalance in actual use.

[0004] Moreover, as aero-engines develop towards higher thrust-to-weight ratios, the dynamics environment faced by the rotor system is increasingly severe, and higher requirements are put forward for vibration control. The traditional manual balancing correction method has been difficult to meet the requirements of modern engine production and maintenance. SUMMARY

[0005] In order to solve the technical defects of the existing rotor imbalance correction method, such as time-consuming operation, dependence on manual experience and professional balancing equipment, and the technical problem that it is difficult to meet the requirements of modern engine maintenance, the application discloses a center of mass automatic adjusting device of a bearing rotor system of an aero-engine. The center of mass automatic adjusting device comprises a circular ring base, the circular ring base is coaxially sleeved on a bearing rotor shaft neck, a plurality of adjusting mechanisms are arranged on the circular ring base in the circumferential direction, a counterweight loading block is arranged on the adjusting mechanism, the distance between the counterweight loading block on each adjusting mechanism and the shaft center of the bearing rotor is adaptively adjusted when the bearing rotor of the aero-engine rotates, so that the shaft center of the bearing rotor and the center of mass are substantially coincident.

[0006] Further, the adjusting mechanism comprises a sliding rod, a spring sheet and a linkage lever mechanism. The sliding rod is arranged on the outer circumferential wall of the circular ring base, the counterweight loading block is arranged on the sliding rod, and the spring sheet is arranged on the sliding rod and located on both sides of the counterweight loading block. One end of each of the spring pieces is fixedly connected to the counterweight loading block, and the other end of one of the spring pieces is fixed to the free end of the slide rod, and the other end of the other spring piece is fixed to the outer peripheral wall of the circular base. One end of the linkage lever mechanism is arranged on the counterweight loading block, and the other end is arranged on the free end of the slide rod.

[0007] Further, the spring piece is a U-shaped spring piece, and both ends of the U-shaped spring piece are provided with through holes through which the slide rod passes.

[0008] Preferably, the spring piece is in a free state when the aero-engine bearing rotor is not rotating, and the spring piece is in a compressed state when the aero-engine bearing rotor is rotating.

[0009] Further, the axial direction of the slide rod is the same as the radial direction of the circular base.

[0010] Further, the linkage lever mechanism comprises a hydraulic structure connected to the counterweight loading block and the slide rod through a scissor-type cross hinge structure.

[0011] Preferably, the scissor-type cross hinge structure comprises a driving arm and a driven arm, the driving arm and the driven arm are connected through a shaft pin to form an X-shaped structure, one end of the driving arm and the driven arm is connected to two ends of the hydraulic structure respectively, the other end of the driving arm is connected to the counterweight loading block, and the other end of the driven arm is connected to the free end of the slide rod.

[0012] More preferably, the free end of the slide rod is provided with a plug, and the other end of the driven arm is fixed to the plug.

[0013] Preferably, the two ends of the hydraulic structure are connected to the driving arm and the driven arm through fixed rods respectively.

[0014] Further, a plurality of lightening holes are uniformly processed on the circular base.

[0015] The device of the present application realizes rotor dynamic self-balancing through the pure mechanical coupling mechanism of centrifugal force-elastic deformation-lever displacement, and has the following beneficial effects compared with the traditional technology: (1) By using the circular base, the slide rod, the counterweight loading block and the adjusting mechanism of the linkage lever mechanism, the position of the centroid deviation can be sensitively perceived during the rotation of the bearing rotor. The spring piece and the linkage lever mechanism timely exert a centripetal force on the counterweight loading block, so that the distance between the counterweight loading block and the center is dynamically adjusted, the unbalance is effectively reduced, the rotor is more accurately balanced and corrected, and the stability of the aero-engine rotor operation is greatly improved, and the vibration and noise caused by unbalance are reduced.

[0016] (2) The traditional rotor balancing method of the aero-engine relies on manual operation, and needs to repeatedly add and adjust the balancing block or remove part of the weight of the rotor, which is complicated and time-consuming, and seriously affects the production and maintenance efficiency of the engine. The application realizes automatic correction of the unbalance of the engine rotor through the innovative design of the structure, reduces the labor cost and time cost. BRIEF DESCRIPTION OF DRAWINGS

[0017] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed in the embodiments will be briefly introduced as follows. Obviously, the drawings in the following description only represent some embodiments of the present application, and all other drawings obtained by those skilled in the art without creative labor based on these drawings also belong to the protection scope of the present application.

[0018] Figure 1 is a schematic view of the centroid automatic adjustment device of the present application; Figure 2 is a schematic view of the centroid automatic adjustment device of the present application assembled on the bearing rotor shaft neck; Figure 3 is a schematic view of the adjustment mechanism of the present application; Wherein, 1, annular base; 2, slide rod; 3, spring sheet; 4, linkage lever mechanism; 5, plug; 6, counterweight loading block; 10, adjustment mechanism; 11, weight reduction hole; 20, bearing rotor shaft neck; 31, arc spring sheet; 32, square spring sheet; 41, hydraulic structure; 42, driving arm; 43, driven arm; 44, shaft pin; 45, fixed rod. DETAILED DESCRIPTION

[0019] The embodiments of the present application will be described in detail below with reference to the drawings.

[0020] The embodiments of the present application will be described in detail below with reference to the drawings.

[0020] The embodiments of the present application will be described in detail below with reference to the drawings.

[0021] In the description of the present embodiment, it needs to be understood that the terms "center", "longitudinal", "transverse", "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing the present invention and simplifying the description, and do not indicate or imply that the devices or elements referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present invention.

[0022] In addition, it also needs to be pointed out that the drawings provided in the following embodiments only illustrate the basic concept of the present disclosure in a schematic manner, and only the components related to the present disclosure are shown in the drawings, not the number, shape and size of the components when actually implemented, and the shape, number and proportion of each component when actually implemented can be arbitrarily changed, and the component layout pattern can also be more complex.

[0023] The present embodiment discloses a center of mass automatic adjustment device of an aero-engine bearing rotor system, referring to Figure 1 and Figure 2 , the center of mass automatic adjustment device comprises a circular ring base 1 coaxially sleeved on a bearing rotor journal 20, a plurality of adjustment mechanisms 10 are arranged on the circular ring base 1 in the circumferential direction, and a counterweight loading block 6 is arranged on the adjustment mechanism 10, the distance between the counterweight loading block 6 on each adjustment mechanism 10 and the shaft center of the bearing rotor is adaptively adjusted when the aero-engine bearing rotor rotates, so that the shaft center of the bearing rotor and the center of mass are kept coincident.

[0024] Referring to Figure 2 , the center of mass automatic adjustment devices are respectively assembled on the front journal and the rear journal of the bearing rotor journal 20, and the center of mass of the bearing rotor can be automatically adjusted by the adjustment mechanism 10 when the bearing rotor rotates, so that the center of mass is always kept coincident with the shaft center.

[0025] Further, referring to Figure 2 , the adjustment mechanism 10 comprises a sliding rod 2, a spring sheet 3 and a linkage lever mechanism 4, the sliding rod 2 is arranged on the outer circumferential wall of the circular ring base 1, the counterweight loading block 6 is arranged on the sliding rod 2, and the spring sheet 3 is arranged on the sliding rod 2 and located on both sides of the counterweight loading block 6.

[0026] One end of each of the two spring sheets 3 is fixedly connected with the counterweight loading block 6, the other end of one of the spring sheets 3 is fixedly connected with the free end of the sliding rod 2, and the other end of the other spring sheet 3 is fixedly connected with the outer circumferential wall of the circular ring base 1; one end of the linkage lever mechanism 4 is arranged on the counterweight loading block 6, and the other end is arranged on the free end of the sliding rod 2.

[0027] Further, referring to Figure 1 and Figure 3 , the spring sheet 3 is a U-shaped spring sheet, both ends of which are provided with through holes through which the slide rod 2 passes. Specifically, referring to Figure 3 , the U-shaped spring sheet includes a circular-arc spring sheet 31, both ends of which are connected with square spring sheets 32, both free ends of the two square spring sheets 32 are provided with through holes through which the slide rod 2 passes. In assembly, the first U-shaped spring sheet is mounted on the slide rod 2 and welded to the circular ring base 1, then the counterweight loading block 6 is sleeved on the slide rod 2 and welded with the first U-shaped spring sheet; then the second U-shaped spring sheet is assembled on the slide rod 2 and welded with the counterweight loading block 6, then the second U-shaped spring sheet is fixed on the free end of the slide rod 2.

[0028] Preferably, the spring sheet 3 is in a free state when the aero-engine bearing rotor is not rotating, and is in a compressed state when the aero-engine bearing rotor is rotating.

[0029] Further, the axial direction of the slide rod 2 is the same as the radial direction of the circular ring base 1.

[0030] Further, referring to Figure 3 , the linkage lever mechanism 4 includes a hydraulic structure 41 connected with the counterweight loading block 6 and the slide rod 2 through a scissor-type cross hinge structure.

[0031] Preferably, referring to Figure 3 , the scissor-type cross hinge structure includes a driving arm 42 and a driven arm 43, the driving arm 42 and the driven arm 43 are connected through a shaft pin 44 to form an X-shaped structure, one end of the driving arm 42 and one end of the driven arm 43 are respectively connected to both ends of the hydraulic structure 41, the other end of the driving arm 42 is connected with the counterweight loading block 6, and the other end of the driven arm 43 is connected with the free end of the slide rod 2. In installation of the linkage lever mechanism, the driving arm 42 and the driven arm 43 are first connected through the shaft pin 44 (also referred to as a fulcrum), then one end of the driving arm 42 and one end of the driven arm 43 are respectively fixed to both ends of the hydraulic structure 41, one end of the driven arm 43 is fixed to the free end of the slide rod 2, and the driving arm 42 is fixed to the counterweight loading block 6.

[0032] More preferably, referring to Figure 3 , in order to prevent the adjustment mechanism and the counterweight loading block 6 from falling off the slide rod 2, a plug 5 is arranged at the free end of the slide rod 2, and the other end of the driven arm 43 is fixed to the plug 5.

[0033] Preferably, referring to Figure 3As shown, the two ends of the hydraulic structure 41 are connected to the active arm 42 and the driven arm 43 respectively via fixed rods 45. In addition, the active arm 42 and the driven arm 43 have the same structure in this invention, both of which are rod-shaped structures with hinge structures connected to their ends.

[0034] Further, see Figure 1 As shown, the annular base 1 has a plurality of weight-reducing holes 11 uniformly machined on it.

[0035] In this invention, the principle of bearing rotor center of mass adjustment is as follows: the center of mass is adjusted towards the geometric center by the positional differences of the counterweight blocks 6 on each adjustment mechanism 10. When the rotor has uneven mass distribution, the counterweight blocks 6 at different positions will slide to different degrees along the slide bar 2 during rotation due to differences in centrifugal force. That is, the counterweight block 6 on the unbalanced side is pushed by a greater centrifugal force and slides a farther distance, while the other side slides a shorter distance due to a smaller force. At the same time, the spring plates 3 and the linkage lever mechanism 4 on both sides of the counterweight blocks 6 generate compression and tension deformations respectively, applying corresponding centripetal forces and dynamically changing the distance between each counterweight block 6 and the geometric center of the bearing rotor. Through the differentiated adjustment of the positions of each counterweight block 6, the mass distribution of the system is redistributed, and finally the center of mass of the bearing rotor is precisely adjusted to the geometric center position, thereby achieving dynamic balance correction.

[0036] The device of the present invention achieves dynamic self-balancing of the rotor through a purely mechanical coupling mechanism of centrifugal force-elastic deformation-lever displacement, which has the following advantages compared with traditional technology: (1) By using an adjustment mechanism consisting of a circular base, a sliding rod, a counterweight loading block, and a linkage lever mechanism, the position of the center of mass deviation can be sensitively detected during the rotation of the bearing rotor. By applying centripetal force to the counterweight loading block in a timely manner through the spring plate and the linkage lever mechanism, the distance between the counterweight loading block and the center of the circle is dynamically adjusted, effectively reducing the imbalance and achieving more precise balance correction of the rotor. This greatly improves the stability of the aero-engine rotor operation and eliminates vibration and noise caused by imbalance.

[0037] (2) Traditional aero-engine rotor balancing methods rely on manual operation, requiring repeated addition and adjustment of balance weights or removal of rotor weights. This process is cumbersome and time-consuming, severely impacting engine production and maintenance efficiency. This invention, through innovative structural design, achieves automatic correction of engine rotor imbalance, reducing both labor and time costs.

[0038] Obviously, those skilled in the art should understand that the above description is only preferred embodiments of the present application, and is not used to limit the present application, and the embodiments of the present application can have various changes and modifications for those skilled in the art. Any modification, equivalent replacement, improvement, etc. within the spirit and principle of the present application shall be included in the protection scope of the present application.

[0039] In addition, it should be understood that although the present specification is described in terms of embodiments, not every embodiment contains only one independent technical solution, and the description of the specification is only for the sake of clarity, and those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be combined appropriately to form other embodiments that those skilled in the art can understand.

Claims

1. An automatic centroid adjustment device for an aero-engine bearing rotor system, characterized in that, The system includes a circular base (1), which is coaxially mounted on the journal of the bearing rotor. Multiple adjustment mechanisms (10) are arranged circumferentially on the circular base (1). Each adjustment mechanism (10) is provided with a counterweight loading block (6). When the aero-engine bearing rotor rotates, the distance between the counterweight loading block (6) on each adjustment mechanism (10) and the axis of the bearing rotor is adaptively adjusted so that the axis of the bearing rotor and the center of mass are kept coincident.

2. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 1, characterized in that, The adjustment mechanism (10) includes a slide rod (2), a spring plate (3) and a linkage lever mechanism (4). The slide rod (2) is disposed on the outer peripheral wall of the circular base (1). The slide rod (2) is provided with the counterweight loading block (6). The spring plate (3) is provided on the slide rod (2) and on both sides of the counterweight loading block (6). One end of each of the two spring plates (3) is fixedly connected to the counterweight loading block (6), and the other end of one of the spring plates (3) is fixed to the free end of the slide rod (2), while the other end of the other spring plate (3) is fixed to the outer peripheral wall of the ring base (1). One end of the linkage lever mechanism (4) is set on the counterweight loading block (6), and the other end is set on the free end of the slide bar (2).

3. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 2, characterized in that, The spring sheet (3) is a U-shaped spring sheet, and both ends of the U-shaped spring sheet are provided with through holes through which the slide rod (2) passes.

4. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 3, characterized in that, When the rotor of the aero-engine bearing is not rotating, the spring plate (3) is in a free state; when the rotor of the aero-engine bearing is rotating, the spring plate (3) is in a compressed state.

5. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 2, characterized in that, The axial direction of the slide bar (2) is the same as the radial direction of the annular base (1).

6. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 2, characterized in that, The linkage lever mechanism (4) includes a hydraulic structure (41), which is connected to the counterweight loading block (6) and the slide rod (2) via a scissor-type cross hinge structure.

7. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 6, characterized in that, The scissor-type cross-hinged structure includes an active arm (42) and a driven arm (43). The active arm (42) and the driven arm (43) are connected by a pivot pin (44) to form an X-shaped structure. One end of the active arm (42) and the driven arm (43) are respectively connected to the two ends of the hydraulic structure (41). The other end of the active arm (42) is connected to the counterweight loading block (6), and the other end of the driven arm (43) is connected to the free end of the slide bar (2).

8. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 7, characterized in that, The free end of the slide bar (2) is provided with a plug (5), and the other end of the driven arm (43) is fixed on the plug (5).

9. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 6, characterized in that, The two ends of the hydraulic structure (41) are connected to the active arm (42) and the driven arm (43) respectively via fixed rods (45).

10. The automatic centroid adjustment device for the rotor system of an aero-engine bearing according to claim 1, characterized in that, The annular base (1) is uniformly machined with multiple weight-reducing holes (11).

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